Ceramic matrix composite airfoil structures for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9915154-B2
Application number	US-201113116093-A
Country	US
Kind code	B2
Filing date	May 26, 2011
Priority date	May 26, 2011
Publication date	Mar 13, 2018
Grant date	Mar 13, 2018

Abstract

A Ceramic Matrix Composite (CMC) airfoil segment for a gas turbine engine includes a box-shape fiber geometry which defines a rectilinear pressure side bond line and a rectilinear suction side bond line.

First claim

What is claimed is:

1. A Ceramic Matrix Composite (CMC) airfoil segment for a gas turbine engine comprising:
a box shape CMC fiber geometry which defines a rectilinear pressure side bond line and a rectilinear suction side bond line, the airfoil segment defines a pressure side portion of a first airfoil and a suction side portion of a second airfoil, wherein said pressure side portion on said airfoil segment is configured to mate with a suction side portion of a second airfoil segment to form said first airfoil.

2. The Ceramic Matrix Composite airfoil segment as recited in claim 1 , wherein each of said rectilinear pressure side bond line and said rectilinear suction side bond line are generally aligned with a leading edge, a trailing edge, an inner platform portion and an outer platform portion.

3. The Ceramic Matrix Composite airfoil segment as recited in claim 1 , wherein said rectilinear pressure side bond line is offset from a trailing edge.

4. The Ceramic Matrix Composite airfoil segment as recited in claim 1 , wherein each of said rectilinear pressure side bond line and said rectilinear suction side bond line are generally aligned parallel to a direction of pull due to centrifugal force.

5. The Ceramic Matrix Composite airfoil segment as recited in claim 1 , wherein each of said rectilinear pressure side bond line and said rectilinear suction side bond line are defined by a portion of a respective airfoil section.

6. The Ceramic Matrix Composite airfoil segment as recited in claim 1 , wherein said rectilinear pressure side bond line is defined along a portion of a pressure side of an airfoil section.

7. The Ceramic Matrix Composite airfoil segment as recited in claim 6 , wherein a rectilinear suction side bond line defined along a portion of a suction side of an adjacent airfoil segment mates with said rectilinear pressure side bond line.

8. The Ceramic Matrix Composite airfoil segment as recited in claim 1 , wherein said rectilinear suction side bond line is defined along a portion of a suction side of an airfoil section.

9. The Ceramic Matrix Composite airfoil segment as recited in claim 8 , wherein a rectilinear pressure side bond line defined along a portion of a pressure side of an adjacent airfoil segment mates with said rectilinear suction side bond line.

10. The Ceramic Matrix Composite airfoil segment as recited in claim 8 , wherein said box shape fiber geometry includes at least one ply of CMC material.

11. The Ceramic Matrix Composite airfoil segment as recited in claim 1 , wherein the pressure side portion includes a pressure side bond surface for mating with a suction side bond surface on the suction side portion of the second airfoil segment.

12. A Ceramic Matrix Composite (CMC) structure for a gas turbine engine comprising:
an outer ring;
an inner ring; and
a multiple of CMC airfoil segments bonded between said outer ring and said inner ring, each of said multiple of CMC airfoil segments of a box shape CMC fiber geometry which defines a rectilinear pressure side bond line and a rectilinear suction side bond line, wherein each of said multiple of CMC airfoil segments includes a pressure side portion having a pressure side bond surface area and a suction side portion having a suction side bond surface area, wherein a pressure side bond surface area of a first airfoil segment mates with a suction side bond surface area of a second airfoil segment to form a first airfoil.

13. The Ceramic Matrix Composite (CMC) structure as recited in claim 12 , wherein said multiple of CMC airfoil segments form an airfoil section within a Low Pressure Turbine ring vane.

14. The Ceramic Matrix Composite (CMC) structure as recited in claim 12 , wherein said multiple of CMC airfoil segments are assembled in an adjacent complementary manner to form a ring of airfoils.

15. The Ceramic Matrix Composite (CMC) structure as recited in claim 12 , wherein said outer ring is a CMC outer ring.

16. The Ceramic Matrix Composite (CMC) structure as recited in claim 12 , wherein said inner ring is a CMC inner ring.

17. The Ceramic Matrix Composite (CMC) structure as recited in claim 12 , wherein said outer ring is a CMC outer ring and said inner ring is a CMC inner ring.

18. A method of assembling a Ceramic Matrix Composite (CMC) structure for a gas turbine engine comprising:
bonding a pressure side bond surface area on a pressure side portion of a first CMC airfoil segment to a suction side bond surface area on a suction side portion of a second CMC airfoil segment at a rectilinear pressure side bond line of the first CMC airfoil segment to form a first airfoil; and
bonding a third CMC airfoil segment to a rectilinear suction side bond line of the first CMC airfoil segment.

19. The method as recited in claim 18 , wherein each of the rectilinear pressure side bond line and the rectilinear suction side bond line are generally located along a leading edge, a trailing edge, an inner platform portion and an outer platform portion.

20. The method as recited in claim 18 , wherein the first CMC airfoil segment and the second CMC airfoil segment each define a box shape fiber geometry.

21. The method as recited in claim 18 , further comprising bonding the first CMC airfoil segment and the second CMC airfoil segment to a CMC outer ring and a CMC inner ring.

22. The method as recited in claim 18 , wherein each of the rectilinear pressure side bond line and the rectilinear suction side bond line are generally located along an inner platform portion and an outer platform portion, the inner platform portion and the outer platform portion defines a complementary edge geometry between the first CMC airfoil segment and the second CMC airfoil segment.

23. The method as recited in claim 18 , wherein the first CMC airfoil segment and the second CMC airfoil segment define a hollow airfoil.

24. The method as recited in claim 18 , including bonding a pressure side bond surface area on a pressure side portion of the third CMC airfoil segment to a suction side bond surface area on a suction side portion of the first CMC airfoil segment at the rectilinear suction side bond line of the first CMC airfoil segment to form a second airfoil.

Assignees

• Berczik Douglas M
• Suciu Gabriel L
• Merry Brian D
• Ioannis Alvanos
• Dye Christopher M
• United Technologies Corp

Inventors

• Berczik Douglas M
• Suciu Gabriel L
• Merry Brian D
• Ioannis Alvanos
• Dye Christopher M

Classifications

• Y10T29/49321

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• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• C04B2237/38

  Fiber or whisker reinforced · CPC title